Space Vehicle System

ABSTRACT

A space vehicle includes: an aerospike nozzle formed on an aft end of the vehicle; a truncated spike including an outer edge and a surface formed on a rear portion of the truncated spike; and an annular ring outlet formed at the aft end of the vehicle between the outer edge of the truncated spike and an inner edge of the aft end of the space vehicle.

CROSS-REFERENCE TO RELATED APPLICATION

This application is a continuation of and claims priority to U.S.Nonprovisional patent application Ser. No. 15/449,921 for a SpaceVehicle System filed on Mar. 4, 2017, the contents of which areincorporated herein by reference in its entirety.

FIELD

This disclosure relates to the field of space vehicle systems. Moreparticularly, this disclosure relates to a space vehicle system havingenhanced characteristics for efficient launch and reentry of the spacevehicle system.

BACKGROUND

Space flight launch vehicles may be either expendable wherein all orsome components of the vehicle are expended after launch of the systemor reusable wherein all or some of the components of the vehicle returnto earth after launch for reuse in later launches. In a reusable system,costs of additional launches may be substantially reduced by reusingcomponents of the initial system. However, a system may be subject toadditional stresses during reentry of the reusable components and thosecomponents must be protected to remain viable for reuse during a laterlaunch.

Typical space flight launch vehicles are shaped for maximum efficiencyduring forward flight of the system, such as during launch. Conventionallaunch vehicles are characterized by elongate cylindrical bodies havinga relatively constant cross-sectional shape from a nose of the vehicleto a tail of the vehicle. This conventional shape induces variousaerodynamic and thermal stresses on the vehicle during launch andflight. Increased stresses on the vehicle may require additionalsupporting structure or thermal resistant materials, thereby increasinga weight of the vehicle.

Conventional launch vehicles are further not typically effective inwithstanding forces on the vehicle during reentry and descent of thesystem. For example, when the launch vehicle descends, variousaerodynamic and thermal loads are placed on a fuselage of the systemthat differ from loads placed on the vehicle during launch and ascent ofthe vehicle. Reinforcing the launch vehicle to withstand loads placed onthe vehicle during reentry and descent may further increase a weight ofthe vehicle, thereby increasing a required fuel load for launch of thevehicle.

What is needed, therefore, is a space vehicle system that has improvedaerodynamic characteristics that increase an aerodynamic efficiency ofthe vehicle during launch and that is capable of withstandingaerodynamic and thermal stress during reentry and descent of thevehicle.

SUMMARY

The above and other needs are met by a space launch vehicle that hasimproved aerodynamic characteristics that increase an aerodynamicefficiency of the vehicle during launch and that is capable ofwithstanding aerodynamic and thermal stress during reentry and descentof the vehicle. In a first aspect, a space launch vehicle is providedincluding: a first section having a surface and expanding in width froma nose end of a space vehicle to a trailing edge of the first section,wherein the first section shields a forward portion of the spacecraftduring launch, ascent and forward flight; a second section having asurface and narrowing in width from a first end adjacent the trailingedge of the first section to a second end distal from the first end,wherein the second section shields the forward portion of the spacecraftduring reentry and descent of the vehicle; a third section having asurface and a first end adjacent to the second end of the second sectionand a second end that is distal from the first end, the third sectionhaving a substantially continuous width along a length of the thirdsection; a fourth section having a surface and expanding in width from afirst end adjacent to the second end of the third section to a tail endof a space vehicle; and a fifth section including a heat shield formedon a tail surface of the space vehicle adjacent to the fourth section.

In one embodiment, the space launch vehicle further includes a shockcone and spike formed on the nose end of the space vehicle. In anotherembodiment, the multi-planar space vehicle fuselage further includes acargo bay located within the third section. In yet another embodiment,the multi-planar space vehicle fuselage further includes one or more airintakes formed in the third surface of the third section.

In one embodiment, a maximum width of the fourth section at the tail endof the space vehicle is wider than a maximum width of the first section.

In another embodiment, the multi-planar space vehicle fuselage furtherincludes cascading isolator plates formed on the surface of the firstsection, the surface of the second section, and the surface of thefourth section. In yet another embodiment, each of the isolator platesincludes a leading surface and a trailing surface, and wherein theleading surface has a slope that is shallower than a slope of thetrailing surface.

In another embodiment, the multi-planar space vehicle fuselage furtherincludes a plurality of landing legs attached to the fuselage.

In one embodiment, the multi-planar space vehicle fuselage furtherincludes a skirt formed around the fuselage adjacent the second end ofthe second section.

In another embodiment, the multi-planar space vehicle further includesan aerospike nozzle formed on an aft end of the vehicle at the fifthsection. In yet another embodiment, the aerospike nozzle includes: atruncated spike including an outer edge and a surface formed on a rearportion of the truncated spike; a plurality of injectors on the surfaceof the truncated spike for emitting a gas from the surface of thetruncated spike into a recirculation region behind the space vehicle;and an annular ring outlet formed on the fifth section between the outeredge of the truncated spike and an inner edge of the fifth section. Inone embodiment, the truncated spike further includes a plurality of heatresistant tiles located on the surface of the truncated spike.

In a second aspect, a space launch vehicle is provided including: ashock cone and spike formed on the nose end of the space vehicle; afirst section adjacent to the shock cone and spike and having a surfaceand expanding in width from a nose end of a space vehicle to a trailingedge of the first section, the first section including a plurality offirst cascade plates formed on the surface at least partially along alength of the first section, wherein the first section shields a forwardportion of the spacecraft during launch, ascent and forward flight; asecond section having a surface and narrowing in width from a first endadjacent the trailing edge of the first section to a second end distalfrom the first end, the second section including a plurality of secondcascade plates formed on the surface at least partially along a lengthof the second section, wherein the second section shields the forwardportion of the spacecraft during reentry and descent of the vehicle; athird section having a surface and a first end adjacent to the secondend of the second section and a second end that is distal from the firstend, the third section having a substantially continuous width along alength of the third section; a fourth section having a surface andexpanding in width from a first end adjacent to the second end of thethird section to a tail end of a space vehicle, the fourth sectionincluding a plurality of fourth section cascade plates formed on thesurface at least partially along a length of the fourth section; and afifth section including a heat shield formed on a tail surface of thespace vehicle adjacent to the fourth section.

In a third aspect, a space launch vehicle is provided including: a shockcone and spike formed on the nose end of the space vehicle; a firstsection adjacent to the shock cone and spike and having a surface andexpanding in width from a nose end of a space vehicle to a trailing edgeof the first section, the first section including a plurality of firstcascade plates formed on the surface at least partially along a lengthof the first section, wherein the first section shields a forwardportion of the spacecraft during launch, ascent and forward flight; asecond section having a surface and narrowing in width from a first endadjacent the trailing edge of the first section to a second end distalfrom the first end, the second section including a plurality of secondcascade plates formed on the surface at least partially along a lengthof the second section, wherein the second section shields the forwardportion of the spacecraft during reentry and descent of the vehicle; athird section having a surface and a first end adjacent to the secondend of the second section and a second end that is distal from the firstend, the third section having a substantially continuous width along alength of the third section; a fourth section having a surface andexpanding in width from a first end adjacent to the second end of thethird section to a tail end of a space vehicle, the fourth sectionincluding a plurality of fourth section cascade plates formed on thesurface at least partially along a length of the fourth section; a fifthsection including a heat shield formed on a tail surface of the spacevehicle adjacent to the fourth section; and cascading isolator platesformed on the surface of the first section, the surface of the secondsection, and the surface of the fourth section.

BRIEF DESCRIPTION OF THE DRAWINGS

Further features, aspects, and advantages of the present disclosure willbecome better understood by reference to the following detaileddescription, appended claims, and accompanying figures, wherein elementsare not to scale so as to more clearly show the details, wherein likereference numbers indicate like elements throughout the several views,and wherein:

FIG. 1 shows a schematic side view of a space vehicle according to oneembodiment of the present disclosure;

FIGS. 2 and 3 show side views of a space vehicle including cascadingplates according to embodiments of the present disclosure;

FIG. 4 shows a bottom view of an aerospike nozzle of a space vehicleaccording to one embodiment of the present disclosure;

FIG. 5 shows a cross-sectional side view of an aerospike nozzle of aspace vehicle according to one embodiment of the present disclosure;

FIG. 6 shows a cross-sectional view of a capsule bay according to oneembodiment of the present disclosure;

FIG. 7 shows a top view of a space launch vehicle according to oneembodiment of the present disclosure; and

FIG. 8 shows a side view of a space launch vehicle according to oneembodiment of the present disclosure.

DETAILED DESCRIPTION

Various terms used herein are intended to have particular meanings. Someof these terms are defined below for clarity. The definitions givenbelow are meant to cover all forms of the words being defined (e.g.,singular, plural, present tense, past tense). If the definition of anyterm below diverges from the commonly understood and/or dictionarydefinition of such term, the definitions below control.

FIG. 1 shows a basic embodiment of a space launch vehicle 10 thatincludes enhanced characteristics for improved efficiency during launchand reentry of the space launch vehicle 10. The space launch vehicle 10is shaped to withstand aerodynamic and thermal stress encountered duringvarious stages of launch and reentry. Aerodynamic characteristics of thespace launch vehicle 10 reduce stresses on at least portions of thespace launch vehicle 10 and allow the space launch vehicle 10 tofunction as a vertical takeoff vertical landing (“VTVL”) reusablesingle-stage-to-orbit (“SSTO”) vehicle.

The space launch vehicle 10 includes a multi-planar fixed geometryplanned fuselage 12 (“MPFGPF”) that defines a shape of the space launchvehicle 10. Surfaces of the fuselage 12 may include a plurality ofisolators to protect the space launch vehicle 10 from stresses duringlaunch and reentry. In addition to a geometry of the space launchvehicle 10, additional systems manage a balance of weight onboard thevehicle and otherwise adjust characteristics of the vehicle to optimizethe vehicle for both launch and reentry flight conditions.

Multi-Planar Fixed Geometry Planned Fuselage

The fuselage 12 of the space launch vehicle 10, as shown in FIG. 1,includes planar surfaces formed on the fuselage that are shaped toresist thermal and aerodynamic stresses on the vehicle 10 during bothlaunch and reentry conditions. The vehicle 10 is formed into sections ofsurfaces on the fuselage 12 that are each shaped withstand aerodynamicand thermal stresses on the vehicle during various stages of launch andreentry.

The fuselage 12 preferably includes a shock cone 14, a first section 16,a second section 18, a third section 20, a fourth section 22, and afifth section 23 formed along a length of the space launch vehicle 10.The sections of the fuselage 12 include surfaces that may be located ona windward side of the vehicle 10 wherein the surfaces are facing a freestream or a leeward side of the vehicle 10 wherein the surfaces areisolated from the free stream. Surfaces of the vehicle 10 may be locatedon a windward side when the vehicle travels in a forward direction, suchas during launch, and may also be located on a leeward side when thevehicle travels in a reverse direction, such as during reentry of thespace launch vehicle 10.

The shock cone 14 is formed on a nose end 24 of the space launch vehicle10. A tip of the shock cone 14 is formed as a tapered and blunt spike 26that initially contacts air as the space launch vehicle 10 is moving ina forward direction, such as during launch of the vehicle 10. The shockcone 14 is tapered and expands in width from the front end 30 to amiddle portion 32 of the shock cone 14. The shock cone 14 is then formedinto a reverse taper wherein the shock cone 14 narrows in width from themiddle portion 32 to an end of the shock cone 14 that is adjacent tofirst section 16 of the fuselage 12.

The first section 16 of the fuselage 12 abuts the shock cone 14. Thefirst section 16 is formed into a tapered cone and includes an outersurface 34 that expands in width from the nose end 24 to a trailing edge36 of the first section 16. The outer surface 34 is oriented as awindward-facing surface when the space launch vehicle 10 is moving in aforward direction such that the leading end 28 of the vehicle 10 firstencounters air during launch, ascent, and flight of the vehicle 10.

The second section 18 of the fuselage 12 abuts the trailing edge 36 ofthe first section 16 and is formed into a reverse-tapered cone such thatan outer surface 38 of the second section 18 narrows in width from afirst end 40 adjacent to the trailing edge 36 towards a second end 42near a midpoint of a length of the fuselage 12. A width of the first end40 of second section 18 at the trailing edge 36 is preferably less thana width of first section 16 at the trailing edge 36 such that aleeward-facing lip 44 is created between the first section 16 and thesecond section 18. The second section 18 tapers in width from the firstend 40 to the second end 42. The second section 18 is preferably slopedat an angle that is shallower than an angle of the slope of the firstsection 16 and preferably has a length that is longer than a length ofthe first section 16, as shown in FIG. 1. The second section 18 tapersto a width that is preferably equal to a width of the third section 20,as discussed in greater detail below.

As shown in FIG. 1, a skirt 45 may be formed around the fuselage 12 ofthe space launch vehicle 10 adjacent the second end 42 of the secondsection 18. The skirt 45 includes a sloped leading edge and asubstantially flat trailing edge. During launch and forward flight ofthe space launch vehicle 10, the skirt 45 protects the third section 20of the fuselage 10 while during descent and landing the flat trailingedge of the skirt 45 may slow a flow of air around the fuselage to aidin braking of the vehicle 10.

The third section 20 preferably includes a substantially flat surfacealong a length of the third section. A first end 46 of the third section20 is located adjacent to the second end 42 of the second section 18.The third section 20 preferably has a diameter that is approximate orequal to a diameter of the second end 42 of the second section 18 suchthat a smooth surface is formed along a transition from the secondsection 18 to the third section 20. The third section 20 is formed intoa substantially continuous cross-sectional width along a length of thethird section 20 to a second end 48 of the third section 20.

The fourth section 22 is formed adjacent to the second end 48 of thethird section 20 and forms a tail section of the fuselage 12. The fourthsection 22 is formed into a tapered cone expanding in diameter from afirst end 50 adjacent to the second end 48 of the third section 20 to asecond end 52 of the fourth section.

The fifth section 23 includes a heat shield 54 is formed on a tailsurface of the fuselage 12 for shielding the vehicle 10 during reentryand descent. The heat shield 54 is located on the tail surface of thevehicle 10 such that during reentry and descent wherein the vehicle 10is travelling in a direction that is reverse from a direction of flightduring launch and ascent, the heat shield 54 is on a windward surface ofthe vehicle 10 and shields the vehicle 10 from thermal loads duringreentry. The heat shield 54 is preferably formed of a plurality of heatresistant tiles, such as reinforced carbon or ceramic tiles placed onthe tail surface of the fuselage 12.

The fourth section 22 preferably includes one or more landing legsformed along the fourth section 22 for supporting the vehicle 10 duringlanding. The landing legs may be formed similar to known existing legsutilized on VTVL vehicles. For example, the landing legs may be foldinglanding legs that are retracted during launch and flight and that areextended during landing of the vehicle 10. While the above descriptioncontemplates the landing legs being located on the fourth section 22 ofthe vehicle 10, it is also understood that the landing legs may bemounted along other sections of the vehicle 10.

The first section 16, second section 18, third section 20, fourthsection 22, and fifth section 23 provide a shape of the vehicle 10 thatreduce drag and increase lift and stability of the vehicle 10 duringboth launch and reentry. During launch and ascent of the vehicle 10, thefirst section 16 faces the flow of air and shields the second section 18and third section 20 from thermal and mechanical stresses. Drag isinduced on the vehicle 10 by the first section 16, while the secondsection 18 creates a region of recirculation such that air along thesecond section 18 moves slower than air along the first section 16. Theregion of recirculation at the second section 18 counteracts draginduced on the first section 16 by pushing against the second section 18and creating lift on the vehicle 10. At least part of the fourth section22 also faces the stream during launch and ascent of the vehicle 10. Aflow of air along the third section 20 is laminar and higher velocitythan a flow along the second section 18, making the third section 20 apreferable location for an air intake 21 for a propulsion system of thevehicle 10. When the vehicle 10 is moving in a forward direction, suchas during launch, ascent, and forward flight, the second section 18 is aleeward surface and an area of recirculation and turbulent air flow. Airflowing along the second section 18 is of lower speed and higherpressure, causing lift on the second section 18 of the vehicle 10 andstabilizing the vehicle 10 during flight.

The shape of the vehicle 10 including the various sections describedherein further induces positive static stability of the vehicle 10.Regions of pressure and recirculation along the fuselage 12 of thevehicle 10 encourage the vehicle 10 to maintain a direction of flightwhen the vehicle 10 is moving in a forward direction.

During reentry and descent of the vehicle 10, the vehicle 10 istravelling in a substantially reverse direction such that the heatshield 54 is facing the flow of air, the fourth section 22 and firstsection 16 are on leeward facing sides of the vehicle 10. Duringdescent, the second section 18 is on a windward side of the vehicle 10and faces the flow of air. Compression, a consequence of the flow of airon the windward-facing second section 18 act to slow a descent of thevehicle 10 during descent.

Cascading Isolator Plates

Referring now to FIGS. 2 and 3, in one embodiment a plurality ofcascading plates 53 are formed on surfaces of the fuselage 12 to isolateportions of the fuselage 12 from friction and thermal and mechanicalloads. The cascading plates 53 are preferably formed on the outersurface 34 of the first section 16 and the outer surface 38 of thesecond section 18, as shown in FIG. 1. The cascading plates 53 are alsopreferably formed on the outer surface 34 of the fourth section 22. Thecascading plates 53 may also be formed on any outer surfaces of anylanding legs or other structures of the fourth section 22 to shieldthose components during launch and reentry. The cascading plates 53 arepreferably formed of a high temperature material for protecting thefuselage 12 from thermal stress on the vehicle 10 during launch andreentry. The cascading plates 53 include a sloped leading surface 55 anda sloped trailing surface 58. The sloped leading surface 55 ispreferably sloped at an angle that is shallower than the sloped trailingsurface 58 of the cascading plates 53.

The cascading plates 53 formed on the vehicle 10 isolate portions of thefuselage 12 from thermal and mechanical loads during ascent and descentand further dissipate heat generated during flight. The cascading plates53 located on surfaces of the vehicle 10 create multiple shock wavesalong portions of the fuselage 12 that isolate portions of succeedingshock cones from oncoming air flow, thereby reducing the total drag andfriction of the isolated portions and collectively to the vehicle 10.The shock cone 14 creates an initial isolation effect prior to aircontacting the first section 16 of the fuselage 12 to create an initialisolation effect before air reaches the cascading plates 53 formed onthe fuselage 12.

Aerospike Nozzle

Referring to FIGS. 4 and 5, the vehicle 10 preferably includes anaerospike nozzle 56 formed on an aft end of the vehicle 10 at the tailsurface of the fuselage 12. The aerospike nozzle 56 preferably includesa truncated spike 57 extending from the aft end of the vehicle 10. Anannular ring outlet 58 is formed between an outer edge 59 of thetruncated spike 57 and an inner edge 60 of the fifth section 23 (FIG.1). In one embodiment, one or more mechanical doors or actuating petalsare located around the annular ring outlet 58 to cover and protect theannular ring outlet 58 during reentry of the vehicle 10. A slopedtrailing edge 65 is formed between an outer surface of the fourthsection 22 and the inner edge 60 of the fifth section 23 to aid inre-attaching a flow of air from the outer surface of the fourth section22 to the truncated spike 57.

A plurality of nozzles 61 are annularly located around the truncatedspike 57 and direct exhaust gases towards the truncated spike 57 and outof the aft end of the vehicle 10. A plurality of injectors 62 are formedon a surface 63 of the truncated spike 57 and are preferably incommunication with a combustion system of the vehicle 10 or other sourceof gas such that fuel, oxidizer, or other gases are emitted from theinjectors 62 into a recirculation region 64 formed behind the truncatedspike 57 during launch and forward flight of the vehicle 10. The surface63 of the truncated spike 57 preferably includes a plurality of heatresistant tiles forming the heat shield 54 to protect the vehicle 10during reentry and descent of the vehicle 10.

During launch and flight of the vehicle 10, oxidizer and fuel arecombusted at the nozzles 61 and the resulting exhaust is directed ontothe truncated spike 57. During flight, a flow of air from the fourthsection 22 of the fuselage 12 recirculates adjacent the fifth section 23and the recirculating flow pushes the exhaust towards the truncatedspike 57. One or more of fuel, oxidizer, and other gases are emittedfrom the injectors 62 into the recirculation region 64 where they may beignited by the exhaust gases, thereby generating additional thrustagainst the surface 63 of the truncated spike 57. While fuel or oxidizerare preferably emitted from the injectors 62 into the recirculationregion 64, it is also understood that various other gases may be emittedfrom the injectors 62 into the recirculation region 64, therebyincreasing pressure in the recirculation region 64.

Capsule Bay and Door

Referring now to FIGS. 6-8, the space launch vehicle 10 further includesa capsule bay 64 located within the fuselage 12 of the space launchvehicle 10. The capsule bay 64 is preferably located along a midpoint ofthe space launch vehicle 10 and encloses a capsule 62 adjacent to a maincargo bay 66. The main cargo bay 66 includes a cargo bay door 67 thatmay either be formed as opposing hinging doors or a single piece doormounted on hinges at one side of the door 67. The capsule bay 64includes a capsule bay door 68 attached to the fuselage with one or moreexplosive bolts 70 and an explosive hinge 72. The capsule 62 is locatedwithin the capsule bay 64 adjacent to a capsule rest 74 for supportingthe capsule 62 within the fuselage 12.

The capsule bay door 68 is configured to be jettisoned in an emergencysuch that the capsule 62 may be ejected from the space launch vehicle10. The explosive bolts 70 and explosive hinge 72 may be activatedduring an abort sequence. Rockets or other propulsion systems mayjettison the capsule bay door 68 from a side of the fuselage 12. Thecapsule 62 may include one or more rockets that are activated to ejectthe capsule 62 out of the side of the space launch vehicle 10 and awayfrom the vehicle 10. The capsule bay door 68 is semicircular in shape,thereby only requiring the capsule bay door 68 to be jettisoned duringan abort sequence for the capsule to be ejected, thereby reducing a sizeand number of components to be jettisoned during abort of a launch orflight sequence.

The space launch vehicle advantageously provides a reusable vehicleconfigured for VTVL wherein a mechanical load and forces primarily acton a single axis along a length of the vehicle. The space launch vehicleincludes enhanced aerodynamic characteristics that allow the vehicle tooperate in both a forward direction during launch and flight and in areverse direction during reentry and descent.

The foregoing description of preferred embodiments of the presentdisclosure has been presented for purposes of illustration anddescription. The described preferred embodiments are not intended to beexhaustive or to limit the scope of the disclosure to the preciseform(s) disclosed. Obvious modifications or variations are possible inlight of the above teachings. The embodiments are chosen and describedto provide the best illustrations of the principles of the disclosureand its practical application, and to thereby enable one of ordinaryskill in the art to utilize the concepts revealed in the disclosure invarious embodiments and with various modifications as are suited to theparticular use contemplated. All such modifications and variations arewithin the scope of the disclosure as determined by the appended claimswhen interpreted in accordance with the breadth to which they arefairly, legally, and equitably entitled.

What is claimed is:
 1. A space vehicle comprising: an aerospike nozzleformed on an aft end of the vehicle; a truncated spike including anouter edge and a surface formed on a rear portion of the truncatedspike; and an annular ring outlet formed at the aft end of the vehiclebetween the outer edge of the truncated spike and an inner edge of theaft end of the space vehicle.
 2. The space vehicle of claim 1, furthercomprising a plurality of injectors on the surface of the truncatedspike for emitting a gas from the surface of the truncated spike into arecirculation region behind the space vehicle.
 3. The space vehicle ofclaim 1, the truncated spike further comprising a plurality of heatresistant tiles located on the surface of the truncated spike.
 4. Aspace vehicle comprising: an aerospike nozzle formed on an aft end ofthe vehicle; a truncated spike including an outer edge and a surfaceformed on a rear portion of the truncated spike; a plurality ofinjectors on the surface of the truncated spike for emitting a gas fromthe surface of the truncated spike into a recirculation region behindthe space vehicle; and an annular ring outlet formed at the aft end ofthe vehicle between the outer edge of the truncated spike and an inneredge of the aft end of the space vehicle.